# TCDS A10SO: Piper Aircraft Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Piper Aircraft Inc.
- Revision: 13
- Revised: August 7, 2006
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23
- Data sheet PDF: https://openairdocs.org/files/sha256/61/ef/61ef5d6e4bc6071918f1511f087665b4a675848cc462cf82f5167cecf102aaeb
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/E685C431D3D2F7A48625720A0054A9BF.0001
- Page: https://openairdocs.org/tcds/A10SO

## Models (3)

As the data sheet lists them.

- PA-36-375
- PA-36-300
- PA-36-285

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
A10SO 
Revision 13 
 Piper Aircraft, Inc 
 
PA-36-285 
PA-36-300 
PA-36-375 
 
August 7, 2006 
 
TYPE CERTIFICATE DATA SHEET A10SO 
 
This data sheet which is a part of Type Certificate No. A10SO prescribes conditions and limitations under which the product for 
which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate Holder Piper Aircraft, Inc. 
 2926 Piper Drive 
 Vero Beach, Florida    32960 
 
Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC A10SO to Piper Aircraft, Inc on August 7, 
2006. 
 
I. - Model PA-36-285, 1 PCLM (Restricted Category Only), Approved August 31, 1972. 
Engine 1 Teledyne Continental 6-285-B or 6-285-C with CMC Injector with fuel flow schedule 
per curve No. 71-12, or  
 1 Teledyne Continental 6-285-BA or 6-285-CA (See NOTE 12 for -BA and -CA  engines) 
with CMC Injector with fuel flow schedule per curve No. 77041.  Propeller drive ratio to 
crankshaft .500:1. 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits For all operations, 4000 r.p.m.   (2000 propeller r.p.m.)     (285 hp) 
 
Propeller and Propeller Limits 1 Hartzell, Hub Model HC-C2YF-1 ( )F, Blade Model F9587A 
 Pitch Setting: High 27° to 29°, Low 18° ± 0.2° at 30" station. 
 Diameter: Not over 95", not under 93". 
    No further reduction permitted. 
 Spinner:  Hartzell A4203 spinner assembly is required. 
 Propeller Governor:  Hartzell Model F-4-6A 
 OR 
 1 Hartzell, Hub Model HC-C3YF-1 ( )F, Blade Model F9684-1 
 Pitch Setting: High 29° to 31°, Low 16.3° to 16.5° at 30" station. 
 Diameter: Not over 95", not under 93". 
    No further reduction permitted. 
 Spinner:  Hartzell A4203-1    (See NOTE 8 for data on spinner.) 
 Propeller Governor:  Hartzell Model F-4-6A 
 
Propeller Limitations Hartzell Model HC-C2YF-1 ( )F only. 
 Avoid continuous operation the ground between 950 and 1150 propeller rpm in wind 
 above 15 mph. 
 
Airspeed Limits (CAS) Maximum operating 135 mph (117 knots) 
 Vfe, Flaps extended 115 mph (100 knots) 
Page No. 1 2 3 4 5 6 7 8 
Rev. No. 13 12 11 12 12 12 12 12

A10SO Page 2 of 8 
 
C. G. Range (+137.25)   at 3000 lb. or less 
 (+140.0) to (+143.2) at  4400 lb. 
 (+148.1 )   at 2600 lb. or less 
 Straight line variation between points given. 
 
2400
2800
3200
3600
4000
4400
LB.
Fuselag e Statio n - Inch
136 140 144 148
137. 25 140. 00 143. 20 148. 10
RES TRICTED
CATEGORY
 
Empty Weight C. G. Range None 
 
Maximum Weight 4400 lb.    (See NOTE 3) 
 
No. of Seats 1 (+196.0) 
 
Maximum Baggage None 
 
Fuel Capacity 89 gallons at (+138.4) (2 wing tanks)  (87 gallons usable) 
 See NOTE 1 for data on unusable fuel. 
 
Oil Capacity 9 quarts  (5 quarts usable) 
 See NOTE 1 for data on system oil. 
 
Manufacturer's Serial Numbers 36-7360001 through 36-7660135 (See NOTE 9). 
 
II. - Model PA-36-300,   1 PCLM   (Restricted Category Only),   December 12, 1974. 
Same as Model PA-36-285 except engine installation. 
 
Engine 1 Lycoming IO-540-K1G5 with one 5th order and one 6th order pendulum damper. 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 r.p.m.    (300 hp) 
 
Propeller and Propeller Limits 1 Hartzell, Hub Model HC-C2YK-1 ( )F, Blade Model F8475R* 
 Pitch Setting: High 29° ± 1°, Low 12° ± 0.2° at 30" station. 
 Diameter: Not over 84", not under 82.3". 
    No further reduction permitted. 
 Spinner:  Hartzell 835-36    (See NOTE 8 for data on spinner.) 
 Propeller Governor:  Hartzell Model F-4-11A 
 
 *HC-()2YK-() propeller installed on a Lycoming engine may be substituted by HC-()-
2YR-() propeller per Hartzell Service Advisory 61

Page 3 of 8 A10SO 
 
Propeller and Propeller Limits OR 
    (continued) 1 Hartzell, Hub Model HC-3YR-1 ( )F, Blade Model F8468A-6 
 Pitch Setting: High 26° ± 1°, Low  11.8° ± 0.2° at 30" station. 
 Diameter: Not over 80", not under 78". 
    No further reduction permitted. 
 Spinner:  Hartzell 835-36    (See NOTE 8 for data on spinner.) 
 Propeller Governor:  Hartzell Model F-4-11A 
 
Airspeed Limits Maximum operating  135 mph CAS, 131 mph IAS 
 V fe, Flaps extended  115 mph CAS, 116 mph IAS 
 
C. G. Range (+137.25)    at 3000 lb. or less 
 (+140.0)  to (+143.2) at 4400 lb. 
 (+148.1)    at 2600 lb. or less 
 Straight line variation between points given. 
 
2400
2800
3200
3600
4000
4400
LB.
Fuselage Statio n - Inch
136 140 144 148
137. 25 140. 00 143 .20 148. 10
RES TRICTED
CATEGORY
 
Empty Weight C. G. Range None 
 
Maximum Weight  4400 lb.    (See NOTE 3) 
 
No. of Seats 1 (+196.0) 
 
Maximum Baggage None 
 
Fuel Capacity 89 gallons at (+138.4) (2 wing tanks)  (86 gallons usable) 
 See NOTE 1 for data on unusable fuel. 
 
Oil Capacity 12 quarts  (9¼ quarts usable) 
 See NOTE 1 for data on system oil. 
 
Manufacturer's Serial Numbers 36-7560001 through 36-8160023 (See NOTES 9 and 13) 
 
 
III. - Model PA-36-375,   1 PCLM   (Restricted Category),   Approved  October 4, 1977. 
Engine 1 Lycoming IO-720-D1CD or Lycoming IO-720-D1C with one 3.5 order, six 4th order 
and one 5th order pendulum damper. 
 
Fuel 100/130 minimum grade aviation gasoline

A10SO Page 4 of 8 
 
Engine Limits For all operations, 2500 r.p.m.    (375 hp) 
 
Propeller and Propeller Limits 1 Hartzell, Hub Model HC-C3YR-1 ( )F, Blade Model F8475R 
 Pitch Setting: High 27° ± 1°, Low 13.3° ± 0.2° at 30" station. 
 Diameter: Not over 86", not under 84". 
    No further reduction permitted. 
 Spinner:  Hartzell 835-36    (See NOTE 8 for data on spinner.) 
 Propeller Governor:  Hartzell F-4-23 
 
Airspeed Limits Maximum operating 135 mph CAS, 135 mph IAS 
 V fe, Flaps extended 120 mph CAS, 124 mph IAS 
 
C. G. Range (+139.00)     at 4800 lb. or less 
 (+139.00) to (+142.15)  at 4800 lb. 
 (+146.70)     at 3200 lb. or less 
 Straight line variation between points given. 
 
2800
3200
3600
4000
4400
4800
LB.
Fusela ge Statio n - Inch
136 140 144 148
139. 00 142 .15 146.70
RES TRICTED
CATEGORY
 
Empty Weight C. G. Range None 
 
Maximum Weight 4800 lb.    (See NOTE 3) 
 
No. of Seats 1 (+196.0) 
 
Fuel Capacity 89 gallons at (+138.4) (2 wing tanks)  (86 gallons usable) 
 See NOTE 1 for data on unusable fuel. 
 
Oil Capacity 17 quarts  (14 quarts usable) 
 See NOTE 1 for data on system oil. 
 
Manufacturer's Serial Numbers 36-7802001 through 36-8302025  (See NOTE 9)

Page 5 of 8 A10SO 
 
DATA PERTINENT TO ALL MODELS 
Datum 126.0 inches forward of the wing leading edge at the intersection of the straight and 
tapered section. 
 
Leveling Means Two screws right side fuselage, inside below window. 
 
Control Surface Movements Aileron (± 1°) Up 20° Down 17° 
 Elevator (± 1°) Up 30° Down 20° 
 Elevator Tabs (+3°, -1°) Up 15.5° Down 22.5°   Elevator Neutral 
 Rudder (± 1°) Left 25° Right 25° 
Flaps (± 1°) Up 0° Down 30°   for PA-36-285 and PA-36-300
 (± 1°) Up 0° Down 20°   for PA-36-375 
 
 See NOTE 10 for flap travel restriction. 
 
Certification Basis FAR 21 dated February 1, 1965, including Amendments 21-1 through 21-24 dated 
February 9, 1969, and FAR 23 dated August 1, 1967, including Amendments 23-1 
through 23-6 dated August 1, 1967, with exception to FAR 23 per FAR 21.25(a)(1). 
 (See NOTE 4) 
 
 Application for Type Certificate dated April 30, 1969. 
 Type Certificate issued August 31, 1972.  Obtained by the manufacturer under delegation 
option procedures. 
 
Production Basis Approved for manufacture of spare parts only under Production Certificate No. 206. 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(see Certification Basis) must be installed in the aircraft for certification.  In addition, the 
following items of equipment are required: 
 
 1. VB-646 issued August 19, 1974, for Model PA-36-285, S/N 36-7360001  
   through 36-7460041. 
 
 2. VB-683 issued January 31, 1975,  for Model PA-36-285, S/N 36-7560001  
   through 36-7660135. 
 
 3. Piper Report 2077 issued February 4, 1977, for Model PA-36-300, S/N  
   36-7560001 through 36-8160023, and for Model PA-36-300, S/N 36-7360001  
   through 36-7460041 with Piper Power Plant Conversion Kit 761 134 per Piper  
   Service Spares Letter No. 346 (See NOTE 13). 
 
 4. Piper Report 2125 issued February 7, 1978, for Model PA-36-375, S/N  
   36-7802001 through 36-8302025. 
 
NOTE 1 Current Weight and Balance Report, including list of  equipment included in certificated empty weight and 
loading instructions when necessary, must be provided for each aircraft at the time of original certification. 
 
 The certificated empty weight and corresponding center of gravity locations must include undrainable system 
oil (not included in oil capacity) and unusable fuel as noted below: 
 
 PA-36-285:  
  Fuel: 12.0 lb. at +138.4 
  Oil: 7.5 lb. at +87.0 
 PA-36-300:  
  Fuel: 18.0 lb. at +138.4 
  Oil: 3.5 lb. at +88.5 
 PA-36-375:  
  Fuel: 18.0 lb. at +138.4 
  Oil: 3.5 lb. at +90.5

A10SO Page 6 of 8 
 
 
NOTE 2 All placards required in the approved Airplane Flight Manual and approved Airplane Flight Manual 
Supplements must be installed in the appropriate locations. 
 
NOTE 3 The PA-36-285 and PA-36-300 have demonstrated satisfactory operation at 4400 lb., and the PA-36-375 at 
4800 lb., in the Restricted Category envelope at sea level under standard day conditions.  Further weight 
increases should not be accomplished in the field. 
 
  The Normal Category maximum takeoff and landing weight is 3900 lb.  Si nce the hopper load is disposable, 
landing in excess of this weight should not be required.  If it is necessary to make a landing at weight over 
3900 lb., the pilot must exercise caution to prevent structural damage to the landing gear and airframe.  The 
takeoff weight should be adjusted also, to suit the runway surface to prevent over-stressing the structure. 
 
NOTE 4 The following exceptions to FAR 23 were granted based on the Restricted Category operating limitations: 
  FAR 23.25(a); 23.77(b); 23.335; 23.337; 23.1505; 23.1507; 23.1545 and 23.1583(a). 
 
  The following portions of FAR 23 were considered inappropriate for the intended agricultural operations: 
  FAR 23.65(b); 23.221; 23.473; 23.479; 23.481; 23.497(a); 23.561(d); 23.721; 23. 723, 23.725; and 23.727. 
 
NOTE 5 PA-36-285 airplane climb performan ce at sea level, standard day, 4400 lb. gross weight, 0° flaps and with 
Piper Dry Materials Dispersal System installed is 338 f.p.m. 
 
 PA-36-300 airplane climb performance at sea level, standard day, 4400 lb. gross weight, 0° flaps and with 
Piper Dry Materials Dispersal System installed is 322 f.p.m.  (two-blade propeller), 349 f.p.m. (three-blade 
propeller). 
 
 PA-36-375 airplane climb performance at sea level, standard day, 4800 lb. gross weight, 0° flaps and with 
Piper Dry Materials Dispersal System installed is 425 f.p.m. 
 
NOTE 6 The PA-36-285 engine installation consists of the basic Teledyne Continental Motors Model 6-285-B, 6-285-
BA, 6-285-C or 6-285-CA engine with Teledyne Continental Customer Specification No. 2. 
 
NOTE 7 Model PA-36-285, S/N 36-7360001 through 36-7460041 are e ligible for multiple airworthiness certification 
in the Restricted and Normal Categories in accordance with FAR 21.187.  Conversion between categories 
may be accomplished in accordance with Piper Report VB-592. 
 
NOTE 8 PA-36-285 aircraft may be operated with Hartze ll A4201-1 spinner dome removed.  Spinner backup plate 
must remain installed. 
 
 PA-36-300 two-blade propeller aircraft may be operated with spinner dome and forward bulkhead removed.  
Piper aft bulkhead P/N 67791 is required for flight. 
 
 PA-36-300 three-blade propeller aircraft may be operated with spinner dome and filler plates removed.  
Hartzell aft bulkhead P/N C-885-3 is required for flight. 
 
 PA-36-375 three-blade propeller aircraft may be operated with spinner dome and filler plate removed.  
Hartzell aft bulkhead P/N C-885-3 or P/N C-4549 is required for flight.

Page 7 of 8 A10SO 
 
NOTE 9  The following serial numbered aircraft are not eligible for import certification to the U.S.: 
 
  Model PA-36-285:  
  36-7360050, 36-7460011, 36-7460012, 36-7460013, 36-7460014, 36-7460015, 36-7560088, 36-7660085,  
  36-7660088, 36-7660091, and 36-7660094. 
  Model PA-36-300:  
  36-7760018, 36-7760034, 36-7760047, 36-7760051, 36-7760055, 36-7760120, 36-7760121, 36-7760123,  
  36-7760125, 36-7760129, 36-7760132, 36-7860010, 36-7860011, 36-7860012, 36-7860043, 36-7860045,  
  36-7860047, 36-7860049, 36-7860050, 36-7860051, 36-7860069, 36-7860071, 36-7860073, 36-7860089,  
  36-7860090, 36-7860091, 36-7860092, 36-7860093, 36-7860094, 36-7860095, 36-7860096, 36-7860097,  
  36-7860098, 36-7860102, 36-7860103, 36-7860104, 36-7860105, 36-7860109, 36-7860111, 36-7860112,  
  36-7860122, 36-7860123, 36-7960001, 36-7960007, 36-7960008, 36-7960009, 36-7960010, 36-7960011,  
  36-7960012, 36-7960013, 36-7960014, 36-7960015, 36-7960016, 36-7960017, 36-7960018, 36-7960019,  
  36-8060002, 36-8060003, 36-8060007, 36-8060010,  36-8060015, 36-8060020, 36-8060021, 36-8060022, 
and 36-8060023. 
  Model PA-36-375:  
  36-7802034, 36-7802050, 36-7802061, 36-7802062, 36-7802063, 36-7802074, 36-7902001, 36-7902002,  
  36-7902003, 36-7902020, 36-7902022, 36-7902024, 36-7902033, 36-7902035, 36-7902037, 36-7902048,  
  36-7902049, 36-7902050, 36-7902051, 36-8002005, 36-8002006, 36-8002011, 36-8002013, 36-8002016,  
  36-8002018, and 36-8002025. 
 
NOTE 10 Wing flap travel on Models PA-36-285 and PA-36-300, S/N 36-7360001 through 36-7460041, is  
 0° (± 1°) Up, and 20° (± 1°) Down. 
 
NOTE 11  The following life limits are required: 
 
  For all PA-36 models:  
  The wing main spar lower attachment bolts, Pipe r P/N 77245-00, must be replaced upon the accumulation of 
  2000 hours time-in-service (TIS) and every 2000 hours TI S thereafter (Ref. Piper Service Bulletin No. 501). 
  The wing main spar upper attachment bolts, Pipe r P/N 77245-00, must be replaced upon the accumulation of 
4100 hours TIS and every 4100 hours TIS thereafter (Reference Piper Service Bulletin 744). 
  The wing carry-through spar fittings, Piper P/N 97713-00, 97713-02 or 97713-03, must be replaced upon the 
accumulation of 4100 hours TIS and every 4100 hours TIS thereafter with P/N 97713-03 (Reference Piper 
Service Bulletin 744). 
  The wing spar fittings, Piper P/N 97712-00, must be replaced upon the accumulation of 4100 hours TIS and 
every 4100 hours TIS thereafter (Reference Piper Service Bulletin 744). 
 
  For Models PA-36-285 and PA-36-300, S/N 36-7360001 through 36-7560003 and 36-7660123 through  
  36-8160023, and Model PA-36-375, S/N 36-7802001 through 36-8302025:  
  The spar carry-through assembly, Piper P/N 97370-00 or P/N 76824-02, as applicable, must be replaced 
upon the accumulation of 4100 hours TIS and every 4100 hours TIS thereafter with P/N 76824-02 
(Reference Piper Service Bulletins 552 and 744). 
 
  For Models PA-36-285 and PA-36-300, S/ N 36-7560056 through 36-8160023 and Model PA-36-375, S/N 
  36-7802001 through 36-8302025:  
  The spar assembly, Piper P/N 97701-00 (Rev. P) and P/N 97701-01 (Rev. P) must be replaced with Piper Kit 
764 393, left spar assembly, and Kit 764 394, right spar assembly, upon the accumulation of 4100 hours TIS 
and every 4100 hours TIS thereafter (Reference Piper Service Bulletin 744). 
 
  For Models PA-36-285 and PA-36-300, S/N 36-7560004 through 36-7660122:  
  The spar carry-through assembly, Piper P/N 76767- 00 must be replaced upon the accumulation of 4000 hours 
TIS with Piper P/N 76824-02;  and P/N 76824-02 must be repalced every 4100 hours TIS thereafter 
(Reference Piper Service Bulletin 744). 
 
  For Models PA-36-285 and PA-36-300, S/N 36-7360001 through 36-7560055:  
  The spar assemblies, Piper P/N 97701-00 (Rev. N or  earlier) and P/N 97701-01 (Rev. N or earlier) must be 
replaced upon the accumulation of 3100 hours TIS with Piper Kit 764 393 (left spar assembly) and Kit 764 
394 (right spar assembly), as applicable;  and Kits 764 393 and 764 394 must be replaced every 4100 hours 
TIS thereafter (Reference Piper Service Bulletin 744). 
 
NOTE 12  Field installation of Teledyne Continental engines 6-285-BA and 6-285-CA require the following:

A10SO Page 8 of 8 
 
 (a) Engine installed in accordance with instruction per Teledyne Continental Kit EQ6534, EQ6535, 
EQ6539 or EQ6540 (Ref. Teledyne Continental Newsletter dated April 4, 1977). 
 (b) Engine cowl modified in accordance with Piper Service Letter No. 774 (Applicable to S/N  
  36-7360001 through 36-7660102). 
 (c) The following Airplane F light Manual (AFM) required: 
 
 Aircraft Serial Numbers AFM  
 36-7360001 through 36-7460041 VB-646 
 36-7560001 through 36-7660102 VB-683 
 
NOTE 13 PA-36-285, S/N 36-7360001 through 36-7660135, may be c onverted to a PA-36-300 upon the installation of  
 Piper Power Plant Conversion Kit 761 134 as specified in Piper Service Spares Letter No. 346.  Airplane 
 Flight Manual, Piper Report 2077 approved February 4, 1977, is required for this installation. 
 
 
 
 
....END....
```

## ADs

None name its models.

## STCs approved under this data sheet (66, first 50)

- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA01147WI](https://openairdocs.org/stc/SA01147WI): Installation of Concorde FLA or VRSLA series batteries in Piper Light Airplanes.. Concorde Battery Corporation
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA477GL](https://openairdocs.org/stc/SA477GL): Installation of hopper gate positive metering device.. Texas Transland LLC
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC
- [STC SA00014CH](https://openairdocs.org/stc/SA00014CH): Installation of a P & W (Canada) Turbopropeller engine (Model PT-6A, -6B, -20, -20A, -20B, or -6/C20)  and Hartzell Propeller (Model HC-B3TN-3 (B, D) Hub and Model T10282 (N) -4R Blades). Turbine Conversions Ltd.
- [STC SA00954WI](https://openairdocs.org/stc/SA00954WI): Installation of Concorde RG Series Batteries in Piper Single Engine Airplanes.. Aero-Mach Wilco LLC
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation
- [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation
- [STC SA00344BO PAGE 2](https://openairdocs.org/stc/SA00344BO%20PAGE%202): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SA04362CH](https://openairdocs.org/stc/SA04362CH): Installation of the uAvionix skyBeacon Automatic Dependent Surveillance-Broadcast (ADS-B) Out. uAvionix Corporation
- [STC SA01435SE](https://openairdocs.org/stc/SA01435SE): Installation of J.P. Instruments (JPI) Primary Engine Data Management System. J. P. Instruments
- [STC SA04424AT](https://openairdocs.org/stc/SA04424AT): Installation of Continental Motors, Inc. (CMI) Shower-of-Sparks  Starting Vibrator Booster Systems. Continental Motors, Inc.
- [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC
- [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley
- [STC SA00780SE](https://openairdocs.org/stc/SA00780SE): Installation of the True Lock Safety Retention Axle Lock Nut System. True Lock LLC
- [STC SA02442AK PAGE 2](https://openairdocs.org/stc/SA02442AK%20PAGE%202): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC
- [STC SA02283SE PAGE 2](https://openairdocs.org/stc/SA02283SE%20PAGE%202): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc.
- [STC SA02402SE PAGE 2](https://openairdocs.org/stc/SA02402SE%20PAGE%202): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc.
- [STC SA3531NM](https://openairdocs.org/stc/SA3531NM): Installing copper electrical cables. (182 S/N 33000 THRU 33842) (8E 833 and UP). Bogert Aviation
- [STC SA03148NY](https://openairdocs.org/stc/SA03148NY): The installation of the Latitude Technologies Corporation S100 Tracking System. Latitude Technologies Corporation
- [STC SA02110CH](https://openairdocs.org/stc/SA02110CH): Installation of a Time Trac Data Recorder. P2 Incorporated
- [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International Inc.
- [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc.
- [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC
- [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc
- [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International
- [STC SA4428NM](https://openairdocs.org/stc/SA4428NM): Installation of Schweizer Phermone aerial application system model No. P.A.A.S. 82.. Herculite Products Inc
- [STC SA00927AT](https://openairdocs.org/stc/SA00927AT): Installation of composite propeller spinner.. TCB Composite Co.
- [STC SA00954AT](https://openairdocs.org/stc/SA00954AT): Installation of composite bulkhead.. TCB Composite Co.
- [STC SA10126SC](https://openairdocs.org/stc/SA10126SC): Installation of Aero Advantage ADV200 series vacuum pump per Aero Advantage Drawing Number ADVMSI 500 latest FAA approved revision.. Aero Holdings Ltd. a Texas limited partnership
- [STC SA09470SC](https://openairdocs.org/stc/SA09470SC): Installation of Starter Indicator light system.. Texas Skyways Inc
- [STC SA2687NM](https://openairdocs.org/stc/SA2687NM): Installation of Truboplus/ Electronics Int'l gauges and switches.. Aero Manufacturing Inc.
- [STC SA02093AK](https://openairdocs.org/stc/SA02093AK): Installation of hourmeter airspeed switch.. Avalaska Inc
- [STC SA00442SE](https://openairdocs.org/stc/SA00442SE): Install vortex generators on wings.. Micro AeroDynamics Inc
- [STC SA8705SW](https://openairdocs.org/stc/SA8705SW): Installation of R25V0N Alternator Control Unit or R2510N Alternator Control Unit or V2510A Over Voltage Sensor.. Tovya Group, Inc
- [STC SA00061LA](https://openairdocs.org/stc/SA00061LA): Installation of JPI digital tachometer.. J P Instruments
- [STC SA00148SE](https://openairdocs.org/stc/SA00148SE): Installation of vortex generators on the wing.. Aeronautical Testing Service Inc.
- [STC SA4221WE](https://openairdocs.org/stc/SA4221WE): Installation of two Albany International dispersion POD, Drawing No. 21940 or 21961.. Ecogen, Inc
- [STC SA1626NM PAGE 2](https://openairdocs.org/stc/SA1626NM%20PAGE%202): Installation of Electronics Int'l Digital EGT/CHT Instruments and accessories. (201 Series). Electronics International
- [STC SA5159NM](https://openairdocs.org/stc/SA5159NM): Installation of chip detector system.. Northwest Aircraft Inc
- [STC SA2350NM PAGE 2](https://openairdocs.org/stc/SA2350NM%20PAGE%202): Installation of Electronics International Inc digital carburetor/outside air temperature gauges. Electronics International
- [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International
- [STC SA4522NM](https://openairdocs.org/stc/SA4522NM): Installation of a Hartzell HC-3YR/1RF/F8483 constant speed propeller.. Johnston Aircraft Svc Inc
- [STC SA2425SO](https://openairdocs.org/stc/SA2425SO): Installation of Chemical Evacuation System to remove residue from the agricultural spray dispersal system.. Paul S Woods
- [STC SA3862NM PAGE 1](https://openairdocs.org/stc/SA3862NM%20PAGE%201): Installation of Electronics International Primary TIT/EGT/CHT instruments, remote switches and associated accessories.. Electronics International

All 66: https://openairdocs.org/tcds/A10SO/stcs.md

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